Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

Batista, Armani; Ross, Mathias; Lietz, Christopher; Hargus, William A.

doi:10.3390/en14123387

Cited by 22 publications

(3 citation statements)

References 51 publications

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“…Fig. 2 [4] is a produced and tested strident rocket engine which shares the similar geometric and theoretical concept as the SABRE, but had been designed only for cold flow testing [10].…”

Section: Prospectsmentioning

confidence: 99%

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Liang¹

2022

HSET

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The variety of propulsion methods will reach their peak efficiencies under certain conditions. This paper will focus on the propulsion methods and different propellant choices for certain usage when designing a vehicle or a stage of a rocket with some altitude limitations, their working principles, applications and challenges. The advantages of multistage design for rocket vehicles and the prospects of advanced engine technology using electricity or solar radiation as its main power source will also be discussed. The cost, payload and other attributes such as the thrust-to-weight ratio of every propulsion concept are the main factors for determining the general performance. MRV is the ideal design for rocket vehicles that are launched from the surface of a planet consider the massive amount of energy it requires to get into the orbit or escape the gravity, but the propulsion system can be various depends on the applications under certain conditions of launching and space travel.

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“…Fig. 2 [4] is a produced and tested strident rocket engine which shares the similar geometric and theoretical concept as the SABRE, but had been designed only for cold flow testing [10].…”

Section: Prospectsmentioning

confidence: 99%

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Liang¹

2022

HSET

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“…A detonation wave is a kind of supersonic combustion wave that consists of shock waves driven by energy release from closely coupled chemical reactions, which has broad application prospects in the field of aerospace propulsion technology [1][2][3][4][5]. As one of the innovative propulsion devices, a pulse detonation engine (PDE) generates thrust by using detonation waves and has attracted great attention due to its simple structure and high thermodynamic cycle efficiency [6][7][8].…”

Section: Introductionmentioning

confidence: 99%

Research on Optical Diagnostic Method of PDE Working Status Based on Visible and Near-Infrared Radiation Characteristics

Huang

Kang

2021

Energies

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Fill fraction not only has a profound impact on the process of deflagration to detonation in pulsed detonation engine, but also affects the propulsion performance in both flight and ground tests. In this paper, a novel optical diagnostic method based on detonation exhaust radiation in visible and near-infrared region within 300–2600 nm is developed to determine the current working state in the gas–liquid two-phase pulsed detonation cycle. The results show that the radiation characteristic in each stage of detonation cycle is unique and can be a good indicator to infer the fill fraction. This is verified experimentally by comparison with the laser absorption spectroscopy method, which utilizes a DFB laser driven by ramp injection current to scan H2O transition of 1391.67 nm at a frequency of 20 kHz. Due to concentrated radiation intensity, time duration reaching accumulated radiant energy ratio of 50% in detonation status would be smaller than 1.2 ms, and detonation status would be easily distinguished from deflagration with this critical condition. In addition, the variation of important intermediates OH, CH, and C2 radicals during detonation combustion are obtained according to the analysis of detonation spectrum, which can also be proposed as a helpful optical diagnostics method for the combustion condition based on C radical concentration. The study demonstrates the feasibility of optical diagnostics based on radiation in visible and near-infrared regions, which could provide an alternative means to diagnose and improve pulsed detonation engine performance.

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“…However, the mechanism and process of mode switching is difficult to be revealed by experiments. Batista et al carried out simulation to explain the mechanism of Descending Modal Transition(DMT) process [24]. They found that critical reactant mixing height is an indicator of detonation wave viability.…”

Section: Introductionmentioning

confidence: 99%

Effects of Reversed Shock Waves on Operation Mode in H2/O2 Rotating Detonation Chambers

Chen

Wang

2021

Energies

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Operation modes are an important topic in the research of Rotating Detonation Chamber (RDC) as it can affect the stability of RDC. However, they have not been discussed in detail due to the limitation of measurement means in experiments. The aim of this research is to investigate the mechanism of different operation modes by numerical simulation. In this paper, a numerical simulation for RDCs with separate injectors is carried out. Different operation modes and mode switching are analyzed. There is a series of reversed shock waves in the flow field. It was found that they have great effects on operation mode and mode switching in RDCs. A reversed shock wave can transit into a detonation wave after passing through isolated fresh gas region where fresh gas and burnt gas distribute alternatively. This shock-to-detonation transition (SDT) phenomenon will influence the ignition process, contra-rotating waves mode and mode switching in RDCs. SDT makes the number of detonation wave increases, resulting in multi-wave mode with one ignition. Moreover, quenching of detonation waves after collision and SDT after passing through isolated fresh gas region are the mechanism of contra-rotating waves mode in RDCs with separate injectors. In addition, when the inlet total temperature increases, a shock wave is easier to transit into a detonation wave. The distance that a shock wave travels before SDT decreases when temperature increases. This will result in mode switching. Therefore, SDT determines that there is a lower bound of detonation wave number.

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Descending Modal Transition Dynamics in a Large Eddy Simulation of a Rotating Detonation Rocket Engine

Cited by 22 publications

References 51 publications

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Principles of Multistage Rocket Vehicle and Concepts of Propulsion Methods for Rocket Applications

Research on Optical Diagnostic Method of PDE Working Status Based on Visible and Near-Infrared Radiation Characteristics

Effects of Reversed Shock Waves on Operation Mode in H2/O2 Rotating Detonation Chambers

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